Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door (12-1) and a door support bracket (22) attached to the landing gear door. The support bracket (22) is attached to aircraft structure (10-1) for pivotal movement about a pivot axis (22-1a) between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly (40) is operatively connected to the door support bracket (22) for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly (50) which assists in pivotal movement of the door support bracket (22) and the gear door (12-1) supported thereby from the closed condition into the opened condition thereof.


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    Title :

    МЕХАНИЗМ УПРАВЛЕНИЯ СТВОРКОЙ ШАССИ ЛЕТАТЕЛЬНОГО АППАРАТА С ИНТЕГРИРОВАННЫМ УЗЛОМ АВАРИЙНОГО УПРАВЛЕНИЯ


    Publication date :

    2018-03-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Russian


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge